An approximate solution for the unsteady loading near the square-shape tip of a wing passing through an oblique gust is obtained in closed form. The aerodynamic theory developed can be used to predict airloads felt by a helicopter blade experiencing a blade/vortex interaction for high blade tip speed and/or for small vertical blade/vortex separation. Under these conditions one can show that the blade's trailing edge has little influence on the character of the chordwise loading at all spanwise sections; thus, the chord may be allowed to extend to infinity in the downstream direction. Therefore, the model considered here is that of a quarter-infinite flat plate wing with side edge passing subsonically through an oblique gust.


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    Titel :

    Aerodynamic theory for wing with side edge passing subsonically through a gust


    Beteiligte:
    Martinez, R. (Autor:in) / Widnall, S. E. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1983-06-01



    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



    Aerodynamic Characteristics of Aircraft Under Side Gust

    Olwi, I. / AIAA | British Library Conference Proceedings | 1994